Reciprocated By Coaxial Screw Patents (Class 416/165)
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Patent number: 12326114Abstract: A fan has a rotating bulge defining a radially outermost point of the rotating cone relative to a rotational axis. The rotating bulge is defined by a radially outwardly extending forward portion leading to the radially outermost point on the bulge and then a radially inwardly extending portion aft of the radially outermost point of the bulge leading into the core engine path within the splitter housing. The core splitter housing has a leading edge, and the bulge radially outermost point being upstream of the leading edge of the splitter housing. The bulge radially outermost point is a first radial distance from a rotational axis, and the leading edge of the splitter housing being at a second radial distance of the rotational axis, and a ratio of the first radial distance to the second radial distance being at least 0.95.Type: GrantFiled: August 15, 2023Date of Patent: June 10, 2025Assignee: RTX CorporationInventors: Michael G. McCaffrey, Anthony R. Bifulco, Daniel B. Kupratis
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Patent number: 12275514Abstract: An electrically actuated propeller pitch control system includes a propeller hub assembly, a propeller assembly, and a crosshead drive system. The propeller hub assembly rotates about the central axis during operation of watercraft. The propeller assembly is configured to selectively rotate a propeller blade. The crosshead drive system includes an electric motor, a transmission, and a lead screw that rotates about the central axis.Type: GrantFiled: September 22, 2023Date of Patent: April 15, 2025Assignee: Rolls-Royce Marine North America Inc.Inventors: Eric Maxeiner, Eric Davis, Donald Ricciuti, Anthony Youst, Michael Schwartz
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Patent number: 12221949Abstract: A Kaplan-type turbine includes a stator part and a rotor part; the stator part having a conduit, configured to convey a water flow towards an impeller having a rotation axis, and a stator of an electric generator, while the rotor part includes: an impeller having in turn: an ogive with at least three blades with variable angular setup with respect to an inclination axis substantially orthogonal to the rotation axis; a rotation shaft bearing the impeller; adjustments for adjusting the setup of the blades, defined inside the ogive and the rotation shaft; a rotor of the electric generator, fixed to the rotation shaft. The adjustments for adjusting the setup of the blade include for each blade: a load-bearing disc, from which one blade develops, which load-bearing disc is constrained to rotate on the ogive around the inclination axis; a lever, fixed to the load-bearing disc and developing radially inside the ogive; a manoeuvring rod, pivoted to the lever and to a drive slider.Type: GrantFiled: November 10, 2022Date of Patent: February 11, 2025Assignee: Zeco Di Zerbaro E Costa E C. S.R.L.Inventors: Davide Turcato, Roberto Migliorini, Francesco De Pretto
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Patent number: 12074483Abstract: A generator for a direct driven wind turbine configured to convert kinetic energy of a main shaft of the wind turbine into electrical energy. The generator includes a generator rotor connectable to the main shaft of the wind turbine and a generator stator, the generator includes a generator housing on which the generator stator is arranged. The generator housing includes a front side facing towards a rotor head of the wind turbine in an installed state of the generator and a rear side facing away from the rotor head in the installed state of the generator. The generator includes at least one front generator bearing arranged at the front of the generator housing and a rear generator bearing arranged at the rear of the generator housing.Type: GrantFiled: December 11, 2020Date of Patent: August 27, 2024Assignee: WEPFER TECHNICS AGInventor: Hans Wepfer
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Patent number: 11946437Abstract: A turbomachinery engine can include a fan assembly with a plurality of variable pitch fan blades. The fan blades are configured such that they define a first VPF parameter and a second VPF parameter. The first VPF parameter is within a range of 0.10 to 0.40 and is defined as the hub-to-tip radius ratio divided by the fan pressure ratio. The second VPF parameter is within a range of 1-30 lbf/in2 and is defined as the bearing spanwise force divided by the fan area. In certain examples, the turbomachinery engine further includes a pitch change mechanism, a vane assembly, a core engine, and a gearbox.Type: GrantFiled: August 12, 2022Date of Patent: April 2, 2024Assignee: General Electric CompanyInventors: Daniel A. Niergarth, Martin Manning, Nicholas M. Daggett, Christopher J. Kroger, Ian F. Prentice
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Patent number: 11674435Abstract: A fan assembly for a gas turbine engine includes a fan disk, a trunnion, an actuation device, a fan blade, and a counterweight assembly. The trunnion is mounted to the fan disk. The actuation device is operably coupled to the trunnion. The fan blade is rotatably attached to the fan disk. The counterweight assembly includes a link arm, a lever arm, a hinge, and a counterweight. The link arm is connected to the trunnion, to the actuation device, or to both. The link arm is configured to drive rotation of the trunnion relative to the fan disk. The hinge is pivotably connected to the lever arm. The lever arm is connected to the link arm and is disposed to rotate about a connection point of the lever arm and the hinge. The counterweight is mounted to the lever arm at a location spaced from the hinge.Type: GrantFiled: June 29, 2021Date of Patent: June 13, 2023Assignee: General Electric CompanyInventors: Nicholas M. Daggett, Gert Johannes van der Merwe, Daniel Alan Niergarth, Brian Lewis Devendorf
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Patent number: 11511854Abstract: An aircraft employs articulated, variable-position electric rotors having different operating configurations and transitions therebetween, as well as variable-pitch airfoils or blades, for generating vectored thrust in the different configurations. Control circuitry generates rotor position signals and blade pitch signals to independently control rotor thrust, rotor orientation and rotor blade pitch of the variable-position rotors in a manner providing (i) the transitions among the operating configurations for corresponding flight modes of the aircraft, which may include both vertical takeoff and landing (VTOL) mode as well as a forward-flight mode, and (ii) commanded thrust-vectoring maneuvering of the aircraft in the different configurations, including tailoring blade pitch to optimize aspects of aircraft performance.Type: GrantFiled: April 26, 2019Date of Patent: November 29, 2022Assignee: Textron Systems CorporationInventors: Sean Marshall Baity, David D. Billingsley, Brad S. Galloway, Richard M. Chapman, Daniel Thomas Otradovec, Graham Schill
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Patent number: 8936438Abstract: An adjusting device is provided for pivoting blades of a rotor via a transmission that is actuatable by a co-rotating, axially-displaceable actuating shaft. The adjusting device includes a roller bearing having a first side or ring that is attachable to the actuating shaft and a second side or ring connected with an actuating body that is non-rotatably supported in a support body. The adjusting device further includes a screw drive that axially displaces the actuating body within the support body to thereby linearly actuate the transmission.Type: GrantFiled: May 27, 2011Date of Patent: January 20, 2015Assignee: Antiebolaget SKFInventors: Thomas Fucks, Jean Pierre Grattler, Laurent Benoit
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Patent number: 8899929Abstract: An adjusting device is provided for pivoting blades of a rotor via a transmission that is actuatable by a co-rotating, axially-displaceable actuating shaft. The adjusting device includes a roller bearing having a first side or ring that is attachable to the actuating shaft and a second side or ring connected with an actuating body that is non-rotatably supported in a support body. The adjusting device further includes a screw drive that axially displaces the actuating body within the support body to thereby linearly actuate the transmission.Type: GrantFiled: May 27, 2011Date of Patent: December 2, 2014Assignee: Antiebolaget SKFInventors: Thomas Fucks, Jean Pierre Grattler, Laurent Benoit
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Patent number: 8876474Abstract: A ram air turbine (RAT) in which a cam follower is operably coupled to turbine blades such that a cam follower position determines turbine blade pitch.Type: GrantFiled: November 4, 2010Date of Patent: November 4, 2014Assignee: Hamilton Sundstrand CorporationInventor: David Everett Russ
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Patent number: 8870539Abstract: The present invention relates to a wind turbine assembly comprising a turbine having turbine blades, said turbine being arranged to generate a rotational energy as the turbine blades are engaged by a wind, characterized in that said wind turbine assembly further comprises an emergency brake that is operationally connected to the turbine blades for pitching the turbine blades towards a rest position by the rotational energy of the turbine, when the emergency brake is activated.Type: GrantFiled: January 7, 2010Date of Patent: October 28, 2014Assignee: XEMC, Xiangtan Electric Manufacturing Group Corporation Ltd.Inventor: Jonas Hallström
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Patent number: 8851849Abstract: A pitch change apparatus is provided for a propeller assembly having a row of propeller blades which rotate around an axis of the assembly. The apparatus has a unison ring which is coaxial with the propeller assembly. The unison ring is movable to drive respective mechanisms for varying the pitch of the blades. The apparatus further has a plurality of pitch lock assemblies circumferentially distributed around the unison ring. Each pitch lock assembly has a free state which allows movement of the unison ring and a locked state which prevents or limits movement of the unison ring and thus prevents or limits variation of the pitch of the blades. The pitch lock assembly moves from the free to the locked state when the assembly receives a signal to lock the blades.Type: GrantFiled: November 26, 2010Date of Patent: October 7, 2014Assignee: Rolls-Royce PLCInventors: Andrew Swift, Antony Morgan
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Patent number: 8777575Abstract: This invention relates to a method and a Propeller Pitch Control Arrangement, comprising a propeller hub (1) having a number of interface fittings (10) for adjustable pitch positioning of a propeller blade, a positioning device (3), within said hub (1), having a number of propeller control interfaces (34) and an actuator arrangement (2, 4, 55) arranged to move and position said positioning device (3) to enable varying pitch for said propeller blades, characterized in—that said actuator arrangement includes a rotatable shaft (2) with threads (20) interacting with mating threads (30) at said positioning device (3), and,—that said rotatable shaft (2) is driven by a motor device (4, 5) positioned adjacent said hub (1).Type: GrantFiled: October 12, 2009Date of Patent: July 15, 2014Assignee: Rolls-Royce AktiebolagInventor: Jan-Olov Forsstrom
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Patent number: 8753085Abstract: A device for changing a pitch of a blade of an impeller/propeller is disclosed. The device includes a linear actuator, a first bearing and a second bearing, allowing a relative axial movement between the first bearing and second bearing. The first bearing is mounted between a supporting structure of the rotor shaft and a non-rotary mechanical element, allowing a relative rotation between the supporting structure and the linear actuator. The second bearing is mounted between the second portion and a lever having a rotary point. Operating the linear actuator leads to an angular movement of the lever causing a change of the pitch of a blade, and when operating the at least one linear actuator, a force is generated that acts upon the non-rotary element, so that the rotor shaft is unaffected by the force.Type: GrantFiled: December 19, 2008Date of Patent: June 17, 2014Assignee: Aktiebolaget SKFInventors: Torbjorn Lovgren, Pontus Claesson
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Patent number: 8444388Abstract: A system of counter-rotating propellers for an aircraft turbine engine including a first and a second propeller, each including a stalling control system for the blades, a rotating actuating mechanism for sliding an element to move the angle of attack of the blades, and a disengaging mechanism for rigidly fixing in rotation the rotating actuating mechanism. The system is designed so that when the disengaging mechanism is engaged, a relative rotation speed is created between the elements and the associated rotating actuating mechanism thereof, bringing the blades into a neutral position thereof for feathering.Type: GrantFiled: March 20, 2009Date of Patent: May 21, 2013Assignee: SNECMAInventor: Francois Gallet
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Patent number: 8439640Abstract: A propeller blade pitch control system includes a propeller hub for mounting at least one propeller blade, and a propeller shaft which rotates about an axis to rotationally drive the propeller hub. A pitch change yoke located within the propeller hub is configured to change a pitch of the at least one propeller blade in response to hydraulic fluid flow to a pitch change actuator. A propeller gearbox includes a first, rear end and a second, forward end located between the first, rear end and the pitch change yoke, and is configured to apply torque to the propeller hub. A hydraulic transfer bearing located between the first, rear end and the second, forward end of the propeller gearbox is operable to selectively permit a flow of hydraulic fluid from at least one hydraulic flow controller to the pitch change actuator.Type: GrantFiled: May 13, 2009Date of Patent: May 14, 2013Assignee: Hamilton Sundstrand CorporationInventors: David V. Arel, Robert H. Perkinson
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Patent number: 8267656Abstract: A variable pitch propulsor system with a propeller pitchlock system which utilizes a follower style pitchlock ballscrew screw which tracks the actuator axial stroke. The pitchlock system transfers the propeller yoke loads, from the ballscrew ballnut to the pitchlock nut allowing the propeller to pitchlock; utilizes the same screw thread lead angle for normal ballscrew back driving operation as well as pitch locking capabilities; provides a single ballscrew which is capable of both being back driven by the ballnut and structurally adequate for reacting the blade loads resulting from any flight condition; and minimizes the requirement of additional rotation and torque transferring interfaces between the ballscrew and pitchlock nut.Type: GrantFiled: March 8, 2006Date of Patent: September 18, 2012Inventors: Paul A. Carvalho, Peter J. Dowd
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Patent number: 6896564Abstract: A motor for driving a propeller is disclosed which has a drive shaft (10) which is coupleable to a propeller shaft (20) by bevel gears (12 and 14) so as to rotate the shaft (20) to in turn rotate propeller blades P of an outboard motor. The drive shaft (20) has an internal concentric shaft (30) which enables the adjustment of the pitch of the propeller blades P by mounting the propeller blades P for rotation about a pitch axis and coupling the mounting (72?) via an integral bevel gear (104) to a bevel gear (102) on the shaft (30). A phase adjustment mechanism (40) is provided for rotating the shaft (30) relative to the shaft (20) to in turn rotate the propeller blades P around the pitch axis to change the pitch of the propeller blades P. The phase adjustment mechanism comprises ring gears (48 and 50), together with planet gears (48) in engagement with a gear on the shaft (30) and planet gears (46) in engagement with a gear (26) on the shaft (20).Type: GrantFiled: February 2, 2004Date of Patent: May 24, 2005Assignee: Aimbridge Pty. Ltd.Inventor: Eric Paul Willmot
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Patent number: 6688926Abstract: A motor for driving a propeller is disclosed which has a drive shaft (10) which is coupleable to a propeller shaft (20) by bevel gears (12 and 14) so as to rotate the shaft (20) to in turn rotate propeller blades P of an outboard motor. The drive shaft (20) has an internal concentric shaft (30) which enables the adjustment of the pitch of the propeller blades P by mounting the propeller blades P for rotation about a pitch axis and coupling the mounting (72′) via an integral bevel gear (104) to a bevel gear (102) on the shaft (30). A phase adjustment mechanism (40) is provided for rotating the shaft (30) relative to the shaft (20) to in turn rotate the propeller blades P around the pitch axis to change the pitch of the propeller blades P. The phase adjustment mechanism comprises ring gears (48 and 50), together with planet gears (48) in engagement with a gear on the shaft (30) and planet gears (46) in engagement with a gear (26) on the shaft (20).Type: GrantFiled: October 12, 2001Date of Patent: February 10, 2004Assignee: Aimbridge Pty Ltd.Inventor: Eric Paul Willmot
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Patent number: 6364610Abstract: A variable-pitch boat propeller has a hub rotatable about a hub axis, a plurality of vanes rotatable on the hub and extending generally radially of the hub axis, and an adjustment element rotatable on the hub about the hub axis and connected to the vanes for pivoting the vanes on the hub. An adjustment knob is pivotal on the hub about the hub axis and interengaging formations on the knob and hub limit angular displacement of the knob on the hub between a pair of end positions so that a limited range of adjustment of the vanes is possible with the knob. The interengaging formations include an axially open groove having a pair of ends constituting abutments and an axially projecting screw head and rotationally fixed relative to the hub and received in the groove. The groove is formed in the knob and the screw head is carried on a yoke rotationally coupled to the hub. The groove is arcuate, centered on the hub axis, and has an arc length of substantially less than 360°.Type: GrantFiled: August 4, 2000Date of Patent: April 2, 2002Assignee: Nasyc Holding S.A.Inventor: Peter Müller
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Patent number: 6071076Abstract: An actuation system which includes apparatus for transferring control signals for varying the blade pitch from a non-rotating member to a rotating member of a gas turbine engine is described. In one embodiment, the engine includes a main disk containing a row of blades, and the disk is coupled to a main shaft which rotates about the engine axis. An actuating disk, or cone, rotates with the main disk, and the torque required to rotate the actuating cone is transmitted through ball splines attached to the main shaft. The ball splines allow transmission of torque between the disk and the cone and at the same time enable the disk and the cone to move axially relative to each other without binding. The actuating cone is supported at one end by the ball splines and at its other end by ball thrust bearings. The ball thrust bearings are pre-loaded to enable the bearings to withstand axial loads in opposite directions.Type: GrantFiled: December 16, 1997Date of Patent: June 6, 2000Assignee: General Electric CompanyInventors: M. Kaleem Ansari, Thomas Moniz, August H. Kramer, Anant P. Singh
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Patent number: 6065933Abstract: A propulsion blade retraction and pitch control apparatus includes a hollow primary drive shaft, a pitch control gear assembly mounted, within a propeller hub, to the primary drive shaft, a radially spaced array of pitch control stub shafts mounted to, in co-operation with, the pitch control gear assembly, so as to be selectively rotatable about corresponding pitch control shaft longitudinal axes upon selective actuation of the pitch control gear assembly, propulsion blades pivotally mounted to the pitch control stub shafts at ends of the pitch control stub shafts radially distal from the pitch control gear assembly, one or two coaxial nested pitch control drive shafts, rotatably co-axially journalled so as to be nested within, and co-axial to, the hollow primary drive shaft, said pitch control drive shaft or shafts selectively rotatable to actuate the pitch control gear assembly.Type: GrantFiled: June 16, 1998Date of Patent: May 23, 2000Inventor: Denver D. Secord
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Patent number: 6042333Abstract: An impeller has a plurality of rotating passageways which can be defined between adjacent blades, the blades having a curved root portion and able to pivot across a part spherical hub to maintain a fine line contact. The passageways have a convergence to improve the efficiency of the impeller. The hub can be split into two relatively rotating portions, with the blades attached to each portion to provide an efficient means to vary the pitch of the blades.Type: GrantFiled: July 25, 1997Date of Patent: March 28, 2000Assignee: Magiview Pty. Ltd.Inventor: Terence Robert Day
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Patent number: 5967753Abstract: A controllable-pitch propeller for a sport-type watercraft has a push rod eccentrically connected to each blade displaceable in a bore of the propeller hub. The push rod is sealed with respect to the end of that bore by a multifold bellows whose radial flange is clamped by a cap of an axial flange of the housing in which the bore is provided.Type: GrantFiled: September 28, 1998Date of Patent: October 19, 1999Inventor: Peter Muller
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Patent number: 5931637Abstract: A propeller is controlled to change pitch at at least two different rates. In one embodiment, an electric motor is provided with a high or low voltage for driving a pitch change mechanism at a high or low change rate. Preferably the rate is selected automatically. Preferably, the high rate is not used unless the current pitch is below a threshold.Type: GrantFiled: January 22, 1996Date of Patent: August 3, 1999Assignee: Something Else Limited Liability CompanyInventor: J. Lance Wheeler
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Patent number: 5779446Abstract: An air driven turbine having variable pitched blades is provided that includes a pitch change mechanism and associated control circuits for automatically adjusting the pitch of the blades during either rotating or non-rotating operational modes of the air driven turbine. The pitch control mechanism includes a resettable overspeed protection device which is directly actuated by an overspeed condition of the turbine and operates independently from the pitch change mechanism to move the blades to a failsafe, feathered, or coarse pitch, low speed position. The pitch control mechanism utilizes a linear actuator in the form of an acme screw drive. The air driven turbine includes a ball ramp thrust bearing for attaching the blades to a hub of the turbine in such a manner that during rotation of the turbine actuation loads on the pitch change mechanism are reduced.Type: GrantFiled: November 7, 1995Date of Patent: July 14, 1998Assignee: Sundstrand CorporationInventors: Jon B. Althof, Shan-Chin Tsai, Teddy L. Jones
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Patent number: 5462410Abstract: Damping and sealing of the quill shaft (30) that transmits torque from one rotating component to another as for example in a pitch change actuator system for aeronautical propellers is provided by an O-ring (40) mounted in the space between the end of ball screw (20) and the flange (41) radially extending from quill shaft (30) and the preload of the O-ring (40) provided by the shims (46) bearing against flange (41) and O-ring (40) which serves to enhance the wearability of splines (26, 28 and 50).Type: GrantFiled: November 10, 1994Date of Patent: October 31, 1995Assignee: United Technologies CorporationInventors: Dale E. Smith, Edward W. Chase, III
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Patent number: 5451141Abstract: Pitch change for a variable pitch propeller or fan of the type utilized in a gas turbine engine is effectuated by the unique application of a bidirectional electrical induction AC motor and an electrical DC induction brake operatively connected to the pitch change actuator. The motor can be utilized in a slip speed range encompassing from a positive slip speed to zero slip speed and negative slip speeds which removes the limitations on the gear ratio.Type: GrantFiled: December 23, 1993Date of Patent: September 19, 1995Assignee: United Technologies CorporationInventors: Paul A. Carvalho, John E. Games, Richard L. Bonnanzio
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Patent number: 5431539Abstract: The pitch change mechanism for a variable pitch propeller blade or Advanced Ducted Propulsor (ADP) interconnecting the pitch change actuator and the propeller blades of the type that includes a trunnion attached to the root of the propeller blade, the connecting mechanism includes in one embodiment a translating ball screw nut interconnecting the trunnion through a yoke and a cooperating sliding pin and arm connector. In another embodiment where a hydraulic piston is included in the pitch change actuator the cylindrical housing supports a plurality of circumferentially spaced pins that are in sliding relationship with a rod attached to the trunnion. The trunnions in both embodiments are extended to make the interconnections. Means are provided to prevent the blades from binding up during pitch change movements. This invention eliminates the heretofore utilized sliding anti-rotation spline and the multiple linkage connectors.Type: GrantFiled: October 28, 1993Date of Patent: July 11, 1995Assignee: United Technologies CorporationInventor: Paul A. Carvalho
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Patent number: 5391055Abstract: The pitch of either a fan or propeller driven by a gas turbine engine is changed by utilizing a pair of impulse turbines interfacing between the stationary and rotating portion of the fan or propeller and utilizing a servo control responding to a desired pitch input signal for actuating the normally inactive impulse turbines during fixed pitch to drive the impulse turbine which in turn is operatively connected through a pitch change actuator to change the pitch in accordance with the input signal.Type: GrantFiled: November 24, 1993Date of Patent: February 21, 1995Assignee: United Technologies CorporationInventor: Paul A. Carvalho
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Patent number: 5282719Abstract: Blade pitch is changed by an actuator that is responsive to the relative rotation of two input members. Blade pitch is not changed when the members are rotated at the same speed. However, blade pitch is changed in one direction when a braking torque is applied to one member, and blade pitch is changed in an opposite direction when a braking torque is applied to the other member.Type: GrantFiled: May 13, 1991Date of Patent: February 1, 1994Assignee: AlliedSignal Inc.Inventors: Frederick B. McCarty, Thomas F. Fitzgibbon
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Patent number: 5199850Abstract: A pitch change system (30) for varying the pitch of the blades (16) of a multi-bladed propulsor (10) comprises a pitch change actuation assembly (40) and a pitch change drive assembly (70) for selectively actuating the pitch change actuation assembly (70) whenever it is desired to change blade pitch. The pitch change actuation assembly (40) comprises a ballscrew (42), a ballscrew nut (44) threadably mounted to the ballscrew (42), and a pitch stop assembly (100) having a retractable feather stop (135) which in its normal position prevents the ballscrew (42) from driving the ballscrew nut (44) to move the blades (16) beyond the coarse pitch setting corresponding to blade feather, but in its retracted position permits the ballscrew (42) to drive the ballscrew nut (44) to move the blades (16) through feather to a desired reverse pitch setting.Type: GrantFiled: July 31, 1991Date of Patent: April 6, 1993Assignee: United Technologies CorporationInventors: Paul A. Carvalho, Edward H. Kusiak
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Patent number: 5141399Abstract: A pitch change actuation system is disclosed for adjusting the pitch of a variable pitch propeller blade (20) rotatably mounted to a hub (10) of the propeller. The pitch change actuator comprises a blade actuation piston (30) operatively connected to the propeller blade (20), a pitchlock piston (50) having a longitudinally directed annular shaft (56) extending therefrom about the shaft (34) of the blade actuation piston (30), pitchlock assembly (130, 140, 150) operatively interconnected between the pitchlock piston (50) and the blade actuation piston (30) for restraining inadvertent blade pitch reduction, bias spring (60) for exerting a preload force against the pitchlock piston (50), and fluid supply conduit (70) operatively interconnected in fluid communication between control valve (100) and the pitch change actuator.Type: GrantFiled: October 18, 1990Date of Patent: August 25, 1992Assignee: United Technologies CorporationInventors: Jerome G. Duchesneau, Robert A. Schwartz
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Patent number: 5042966Abstract: A pitch control system has a main electronic control, a mechanical back-up control and a switching system for transferring pitch control from the electronic to the mechanical control in the event of electronic control failure. The switching system utilizes a switch for comparing the output of the electronic and mechanical control systems, the switch choosing the mechanical system if a failure occurs in the electronic control system. By utilizing the switching system, a failure of the electronic control does not permit the blades to go to feather. In certain failure modes, an enable valve or an enable solenoid locks out the switch, to ensure mechanical pitch change control.Type: GrantFiled: December 26, 1989Date of Patent: August 27, 1991Assignee: United Technologies CorporationInventors: Robert A. Schwartz, Paul Carvalho, Robert J. Lampeter
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Patent number: 5037271Abstract: A pitch control system has a main electronic control, a mechanical back-up control and a switching system for transferring pitch control from the electronic to the mechanical control in the event of electronic control failure. The switching system utilizes a switch for comparing the output of the electronic and mechanical control systems, the switch choosing the mechanical system if a failure occurs in the electronic control system. In certain failure modes, an enable solenoid simultaneously locks out the switch, to ensure mechanical pitch change control, and resets the mechanical back-up control to provide a lower degree of pitch control than conventional back-up controllers.Type: GrantFiled: December 26, 1989Date of Patent: August 6, 1991Assignee: United Technologies CorporationInventors: Jerome G. Duchesneau, Robert A. Schwartz
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Patent number: 4753572Abstract: A mechanical pitch lock includes a pitch lock screw (60) that simultaneously rotates within an actuator (42) while the actuator moves to change the pitch of a propeller blade (16). While rotating simultaneously with the motion of the pitch actuator, the pitch lock screw maintains a longitudinal position allowing the actuator to move. If the pitch lock screw does not rotate simultaneously with the actuator, the pitch lock screw moves longitudinally with the actuator until it abuts a projection 66 thereby preventing further movement by the actuator.Type: GrantFiled: October 2, 1986Date of Patent: June 28, 1988Assignee: United Technologies CorporationInventor: Edward H. Kusiak
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Patent number: 4750862Abstract: A modular, easily replaceable, pitch actuation system is removably secured within the hub of an aircraft. The modular system houses a driving system which provides a rotational output to set the pitch of propeller blades mounted to the hub, and a pitch changing system that controls the driving system. The driving system includes a high-speed, low-torque hydraulic motor that drives an harmonic drive to amplify the torque of the motor. The pitch changing system includes an actuator which positions a valve that controls the hydraulic motor, and a nulling gear which repositions the valve and acts as a pitch lock.Type: GrantFiled: November 28, 1986Date of Patent: June 14, 1988Assignee: United Technologies CorporationInventors: Philip E. Barnes, Edward H. Kusiak
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Patent number: 4671737Abstract: Overspeed conditions in a ram air turbine are eliminated through a novel blade pitching mechanism. The mechanism includes a rotatable shaft with a hub mounted thereon for rotation therewith. The hub rotatably mounts at least one blade and a hollow blade pitch control shaft extends generally concentrically about the rotatable shaft and is mounted for reciprocating movement in a path toward and away from the hub. A reciprocating to rotary motion converting mechanism interconnects the control shaft and the blade so that the pitch of the blade can be controlled by controlling the position of the control shaft in the path. A first motor is provided for incrementally moving the control shaft within the path and a second motor is provided for rapidly moving the control shaft within the path to a position therein corresponding to a feathered position of the blades.Type: GrantFiled: December 26, 1984Date of Patent: June 9, 1987Assignee: Sundstrand CorporationInventor: John W. Whitehouse
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Patent number: 4591313Abstract: A plurality of propeller blades are mounted to an axially elongated tubular propeller hub (H1). Each blade is rotatable in position about a radial axis. An electromechanical linear actuator (A1) is housed within the hub for rotating the blades to change their pitch. The actuator includes a rod member (R1) fixed in position relative to the hub, a casing (C1) which can extend and retract relative to the rod member, a rotary electric motor (M1), and a planetary screw drive (SD1). The screw drive (SD1) drivingly interconnects the electric motor (M1) with the casing (C1) for causing the casing to move axially in response to operation of the motor. The actuator (A1) is connected to the propeller (P1) by a linkage (L1) so that movement of the casing causes the propellers to change their pitch. A second actuator (A2) may be housed within the hub (H1) and connected to the first actuator (A1) for providing redundancy in the event of failure of the first actuator.Type: GrantFiled: December 30, 1983Date of Patent: May 27, 1986Assignee: The Boeing CompanyInventors: Henry J. Miyatake, Seiya Sakurai
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Patent number: 4523891Abstract: A propeller pitch change actuation system comprises an input actuator (230) driving a ball screw (200). Operation of the ball screw rotates a torque tube (140) about the longitudinal axis thereof to drive a screw 145 and control valve 120 which controls the pressurization of pitch change actuator (87). Actuator (87) is supplied with hydraulic fluid through the interior of the torque tube.Type: GrantFiled: June 15, 1983Date of Patent: June 18, 1985Assignee: United Technologies CorporationInventors: Robert A. Schwartz, Jerome G. Duchesneau
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Patent number: 4490093Abstract: A windpower system includes a support and a turbine having a shaft rotatively mounted to the support. The turbine has variable pitch blades whose pitch is controlled by the differential motion of a rotary control shaft coaxial with the turbine shaft and the turbine shaft itself so that the blade pitch can be varied by a stationary motor without requiring any slip rings or other such wear-prone couplings. In the event of a power failure, rotary motion of the control shaft is prevented so that the turbine blades are feathered solely due to the force developed by the rotating turbine. Also, if the turbine is used to generate electrical power, an induction generator coupled to the turbine shaft is employed whose shaft speed is indicative of generator output power.Type: GrantFiled: July 13, 1981Date of Patent: December 25, 1984Assignee: U.S. Windpower, Inc.Inventors: Allan Chertok, John Gjertsen, Sr., Louis Manfredi
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Patent number: 4066911Abstract: A sail-type wind-driven prime mover is provided in which the area of the sails facing into the wind is adjustable. The prime mover comprises a drive shaft from which depend radially extending front and rear masts which support flexible sails. The area of the sails facing into the wind can be varied by moving the rear masts along and about the drive shaft while keeping the front masts fixed relative to the drive shaft. In a preferred embodiment in which the prime mover drives an electric generator, means are provided to automatically adjust the sails as a function of the output voltage of the generator.Type: GrantFiled: October 4, 1976Date of Patent: January 3, 1978Inventor: Douglas P. Sarchet
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Patent number: 3994128Abstract: An improved actuating mechanism is provided for a gas turbine engine incorporating fan blades of the variable pitch variety, the actuator adapted to rotate the individual fan blades within apertures in an associated fan disc. The actuator includes means such as a pair of synchronizing ring gears, one on each side of the blade shanks, and adapted to engage pinions disposed thereon. Means are provided to impart rotation to the ring gears in opposite directions to effect rotation of the blade shanks in response to a predetermined input signal. In the event of system failure, a run-away actuator is prevented by an improved braking device which arrests the mechanism.Type: GrantFiled: May 21, 1975Date of Patent: November 30, 1976Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Robert H. Griswold, Jr., Carl L. Broman